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At an instant of time, a satellite in an elliptical orbit is at a distance of 500 km from the surface of the earth. If the semi major axis of the orbit is 8500 km in length, determine the magnitude of the satellite velocity. Take μ = 3.986 x 1014 m3/sec2.

Correct Answer: 8311.38 m/s
u = 1/2 u = 1/2 = 8311.38 m/s.

What is the area swept by a satellite in an elliptical orbit around earth at t = T/5, where T is the time period of the orbit? Given, semi-major axis and semi-minor axis of the orbit are 9,000 km and 4,000 km respectively.

For an eccentricity of 0.92 and semi major axis length of 9500 km, determine the apogee velocity for a satellite in elliptical orbit. Take μ = 3.986 x 1014 m3/sec2.

What is the specific angular momentum of an elliptical orbit, if the flight path angle of the satellite in orbit at an instant is 15°? The satellite is travelling at a velocity of 10.7 km/s at the same instant and is parked at an altitude of 7048 km measured from earth’s center.

What is the specific angular momentum of an Iridium satellite if the orbit is in an elliptical orbit that has a semi-major axis and eccentricity of 46,000 km and 0.85 respectively. Gravitational parameter of earth is 398,600 km3/s2?

What is the apogee velocity of a spacecraft in an elliptical orbit if the eccentricity and semi-major axis of the orbit are 0.9 and 50,000 km2/s respectively?

What is the perigee velocity of a spacecraft in an elliptical orbit if the eccentricity and semi-major axis of the orbit are 0.9 and 50,000 km respectively?

Consider the following statements.
1. The time period of satellite does not depend on the radius of the orbit.
2. The orbital velocity is inversely proportional to the square root of the radius of the orbit.
3. The orbital velocity of a satellite increases with the radius of the orbit.
Which of the statement(s) given above is/are correct?

A plate with an elliptical hole in the centre, with semi-major axis (a) perpendicular to the direction of loading and semi-minor axis (b) along the direction of loading, is subjected to a pull P. The maximum stress induced at the edge of the hole is equal to (where $$\sigma $$ = Stress for a plate with no hole i.e. nominal stress)

If the standard gravitational parameter of earth, μ is 398,600 km3/s2 and the radius of earth is 6378 km, what is the period of a satellite revolving around earth in a circular orbit 500 kms above the surface of the earth?

A spacecraft in an elliptical orbit around earth has perigee radius of 7,900 km and apogee radius of 73,000 km, what is its semi-major axis?